EP1910647B1 - Procédé de montage d'un élément de sécurité sur un rotor de turbomachine - Google Patents

Procédé de montage d'un élément de sécurité sur un rotor de turbomachine Download PDF

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Publication number
EP1910647B1
EP1910647B1 EP06761823A EP06761823A EP1910647B1 EP 1910647 B1 EP1910647 B1 EP 1910647B1 EP 06761823 A EP06761823 A EP 06761823A EP 06761823 A EP06761823 A EP 06761823A EP 1910647 B1 EP1910647 B1 EP 1910647B1
Authority
EP
European Patent Office
Prior art keywords
securing element
rotor
tool
blades
securing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
EP06761823A
Other languages
German (de)
English (en)
Other versions
EP1910647A1 (fr
Inventor
Alexander Böck
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
MTU Aero Engines AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines GmbH, MTU Aero Engines AG filed Critical MTU Aero Engines GmbH
Publication of EP1910647A1 publication Critical patent/EP1910647A1/fr
Application granted granted Critical
Publication of EP1910647B1 publication Critical patent/EP1910647B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

  • the invention relates to a method for mounting a securing element on a turbomachine rotor, in particular on a gas turbine rotor.
  • Rotors of a turbomachine such as gas turbine rotors
  • the blades can either be an integral part of the rotor body or be anchored via blade roots in one or more grooves of the rotor body.
  • Rotors with integral blading are referred to as blisk or bling, depending on whether a disk-shaped or an annular rotor body is present.
  • blisk or bling depending on whether a disk-shaped or an annular rotor body is present.
  • rotors in which the blades are anchored via blade roots in a groove a distinction is made between rotors in which the blade roots of the blades are mounted either in so-called axial grooves of the rotor body or in a so-called circumferential groove thereof.
  • the present invention relates to a rotor of a turbomachine, in particular a gas turbine rotor, in which the blades are fastened via their blade roots in grooves which run at least predominantly in the axial direction of the rotor body, ie in axial grooves.
  • the locking elements are in turn secured in position in the annular grooves via at least one securing element or a locking plate, wherein the or each securing element is inflected into the annular grooves of the rotor body and the rotor blades in a free space between two adjacent locking elements.
  • the document EP 0 609 979 A1 relates to a balanced rotor for a gas turbine engine.
  • balancing elements weight-adapted locking or securing elements are used.
  • FIG. 3 of this document securing elements (Item 29), which have a curved central portion. After snapping into the associated grooves, the elements are preferably formed flat by hammering and thereby radially elongated.
  • the document EP 0 761 930 A1 discloses locking and securing elements (Pos. 27), which have a central portion defined by a recess. It is stated that the last to be mounted securing elements are bent, positioned and then formed flat with a tool. See the Figures 3 and 6 of the document.
  • Locking elements are known which are not deformed, but are secured for example by means of additional spring wires.
  • the present invention is based on the problem to provide a novel method for mounting a securing element on a turbomachine rotor. This problem is solved by a method according to claim 1.
  • the securing element is bent back after being bent or snapped in using a stamp-like tool such that the stamp-like tool is pressed against the center section of the securing element defined by a recess and overbends the middle section in a defined manner.
  • the stamp-like tool is pressed exclusively in the central portion at a distance from both end portions of the securing element, wherein the central portion is plastically deformed in areas on which edge portions of the tool rest.
  • FIG. 1 to 3 a known from the prior art gas turbine rotor with at least predominantly extending in the axial direction of grooves - so-called axial grooves - guided blade feet of blades are described.
  • Fig. 1 and 2 show sections of a known from the prior art gas turbine rotor 10 having a rotor body 11 and a plurality of blades 12.
  • Each of the rotor blades 12 has an airfoil 13 and a blade root 14.
  • a plurality of axial grooves 15 extending in the axial direction are introduced into the rotor base body 11, each rotor blade 12 being anchored with its blade root 14 in such an axial groove 15 in the rotor base body 11.
  • locking elements 16 and securing elements 17 are also referred to as Locking Plates, the locking elements 16 as Retaining Plates.
  • the blades 12 carry portions of an outer shroud 18, wherein the blades 12 are connected together in the region of the outer shroud 18 via a so-called Z-toothing.
  • the locking elements 16 and the securing elements 17 are guided in the assembled state of the gas turbine rotor 10 in annular grooves, namely in an annular groove 19 of the rotor base body 11 and in an annular groove 20 of the rotor blades 12th
  • Fig. 1 In order to introduce the locking elements 16 in the annular grooves 19 and 20 of the rotor body 11 and blade 12 are, as in particular Fig. 1 can be removed, some blades 12 tilted in the direction of the arrows 21 in the circumferential direction, so that positioned therebetween blades 12 are moved in the direction of the arrows 22 in the axial direction can.
  • the blades displaced in the axial direction thus interrupt the annular groove 20 thereof or release the annular groove 20 in such a manner that the locking elements 16 can be inserted or threaded into the annular grooves 19 and 20. After threading the locking elements 16 are at selected circumferential positions (see Fig.
  • FIG. 4 an inventive securing element 23 for securing the position of the rotor blades 12 in the axial grooves 15 of the rotor base body 11 is shown prior to its installation.
  • the securing element 23 according to the invention has a plate-shaped base body 24, wherein the base body 24 has an approximately central recess 25.
  • the recess 25 is formed between two end portions 26 and 27 of the base body 24 and defines a central portion 28 thereof.
  • the securing element 23 according to the invention has mutually parallel bearing surfaces 29 and 30.
  • the two end sections 26 and 27 have aligned contact surfaces 29 and 20 prior to assembly.
  • the central portion 28 is not arched prior to assembly.
  • Such a securing element 23 according to the invention can be used analogously in the case of assembly Fig. 3a to 3b between annular grooves 19 and 20 of rotor base body 11 and blades 12 are bent under elastic and plastic deformation of the securing element 23, wherein after the bending of the securing element 23 the same in Fig. 5 shown position or shape occupies.
  • the bearing surfaces 29 and 30 are curved, as well as the central portion 28th
  • Fig. 6 shows a punch-like tool 33 pressed onto the central portion 28 of the securing element 23, wherein the central portion 28 and the punch-like tool 33 are dimensioned such that the punch-like tool 33 exclusively in the central portion 28 at a distance from the end portions 26 and 27 of the securing element 23 at the same takes effect.
  • the punch-like tool 33 With the help of the punch-like tool 33, the fuse element 23 bent back so that the securing element 23 is bent over in the central portion 28, so that after removing the punch-like tool 33, the securing element 23 in Fig. 7 shown position occupies.
  • the securing element 23 is doing in the central portion 28 in areas 34 and 35, at which edge portions of the punch-like tool 33 are effective to form the in Fig. 7 shown overbending section 31 plastically deformed.
  • the bearing surfaces 29 and 30 of the end portions 26 and 27 are parallel again to each other, so that the same cursing again after bending back.
  • the bearing surfaces 29 and 30 of the end portions 26 and 27 take after the bending back of the securing element 23 therefore again in Fig. 4 shown position.
  • the middle section 23 remains after removal of the punch-like tool 33, the already mentioned, curved overbend section 31st
  • Fig. 4 to 8 can be removed, has the securing element 23 according to the invention in the region of the end portion 27 via a projection 36.
  • This projection 36 is how Fig. 8 can be removed, threaded in the assembly of the fuse element according to the invention in the annular groove 19 of the rotor body 11.
  • the projection 36 is dimensioned such that a center of gravity 37 of the securing element 23 according to the invention is offset relative to a radial abutment 38 of the end portion 26 in the annular groove of the blade root 12 such that in operation acting on the securing element 23 centrifugal forces the projection 36 against a sealing surface 32nd Press in the region of the annular groove 19 of the rotor body 11. This results in an optimized sealing effect for the securing element 23 according to the invention.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un élément de fixation destiné à fixer la position d'aubes mobiles dans des rainures, s'étendant essentiellement de façon axiale, d'un corps de base de rotor d'une turbomachine, comportant un corps de base (24) en forme de plaque. Le corps de base (24) présente un évidement (25) essentiellement central formé entre deux sections terminales (26, 27) du corps de base (24), définissant une section centrale (28) du corps de base (24), s'étendant entre les deux sections terminales (26, 27), les deux sections terminales (26, 27) présentant des surfaces d'appui parallèles (29, 20).

Claims (1)

  1. Procédé de montage d'un élément de sécurisation (23) comportant un tronçon central (28), défini par un évidement (25), et des tronçons d'extrémité (26, 27) sur un rotor de turbomachine, pour sécuriser la position d'aubes dans des rainures, dirigées au moins essentiellement dans une direction axiale, d'un bâti du rotor de turbomachine, l'élément de sécurisation (23) étant recourbé ou encliqueté, par déformation plastique et élastique avec les tronçons d'extrémité (26, 27), dans des rainures annulaires (19, 20) du bâti de rotor (11) et des aubes (12) entre deux éléments de verrouillage (16) distants l'un de l'autre le long de la périphérie, l'élément de sécurisation (23) étant ensuite redressé le plus possible par recourbement en sens inverse et l'élément de sécurisation (23), après le courbement ou l'encliquetage, étant redressé avec un outil (33) type poinçon de telle manière que l'outil (33) type poinçon soit pressé contre le tronçon central (28), défini par un évidement (25) de l'élément de sécurisation (23), et que le tronçon central (28) soit en même temps forjeté de façon définie de sorte que, une fois l'outil (33) type poinçon retiré, les tronçons d'extrémité (26, 27) de l'élément de sécurisation (23) viennent se plaquer de manière définie dans les rainures annulaires (19, 20),
    caractérisé en ce que
    l'outil (33) type poinçon est pressé exclusivement dans le tronçon central (28) à distance des deux tronçons d'extrémité (26, 27) sur l'élément de sécurisation (23), le tronçon central (28) étant déformé de façon plastique dans les zones (34, 35) sur lesquelles des tronçons marginaux de l'outil (33) reposent.
EP06761823A 2005-07-30 2006-07-19 Procédé de montage d'un élément de sécurité sur un rotor de turbomachine Expired - Fee Related EP1910647B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102005035901A DE102005035901A1 (de) 2005-07-30 2005-07-30 Sicherungselement
PCT/DE2006/001246 WO2007014543A1 (fr) 2005-07-30 2006-07-19 Element de fixation d'aubes mobiles

Publications (2)

Publication Number Publication Date
EP1910647A1 EP1910647A1 (fr) 2008-04-16
EP1910647B1 true EP1910647B1 (fr) 2011-09-07

Family

ID=37110385

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06761823A Expired - Fee Related EP1910647B1 (fr) 2005-07-30 2006-07-19 Procédé de montage d'un élément de sécurité sur un rotor de turbomachine

Country Status (4)

Country Link
US (1) US8128374B2 (fr)
EP (1) EP1910647B1 (fr)
DE (1) DE102005035901A1 (fr)
WO (1) WO2007014543A1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2918106B1 (fr) * 2007-06-27 2011-05-06 Snecma Dispositif de retenue axiale d'aubes montees sur un disque de rotor de turbomachine.
DE102008013118B4 (de) * 2008-03-07 2014-03-27 Man Diesel & Turbo Se Anordnung zum Befestigen von Turbinenschaufeln
US8753090B2 (en) * 2010-11-24 2014-06-17 Rolls-Royce Corporation Bladed disk assembly
WO2014137435A2 (fr) * 2013-03-05 2014-09-12 Rolls-Royce North American Technologies, Inc. Procédé de rétention de plaques de capot segmentées de turbine
EP2986824B1 (fr) 2013-04-18 2020-05-27 United Technologies Corporation Amortisseur à minidisque de turbine pour turbine à gaz
GB2511584B (en) 2013-05-31 2015-03-11 Rolls Royce Plc A lock plate
JP6218232B2 (ja) * 2014-03-14 2017-10-25 本田技研工業株式会社 タービンホイール
GB201604473D0 (en) 2016-03-16 2016-04-27 Rolls Royce Plc A bladed rotor arrangement and a lock plate for a bladed rotor arrangement

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3045329A (en) * 1959-07-30 1962-07-24 Gen Electric Method for assembling tongue-and-groove members with locking keys
FR2419389A1 (fr) 1978-03-08 1979-10-05 Snecma Perfectionnements aux flasques de rotors de turbomachines
US5211407A (en) 1992-04-30 1993-05-18 General Electric Company Compressor rotor cross shank leak seal for axial dovetails
GB9302064D0 (en) 1993-02-03 1993-03-24 Rolls Royce Plc Balanced rotor
GB9517369D0 (en) * 1995-08-24 1995-10-25 Rolls Royce Plc Bladed rotor

Also Published As

Publication number Publication date
US20090092497A1 (en) 2009-04-09
EP1910647A1 (fr) 2008-04-16
WO2007014543A1 (fr) 2007-02-08
DE102005035901A1 (de) 2007-02-01
US8128374B2 (en) 2012-03-06

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